CN103112584B - dual mode rotor hub assembly - Google Patents
dual mode rotor hub assembly Download PDFInfo
- Publication number
- CN103112584B CN103112584B CN201210409284.0A CN201210409284A CN103112584B CN 103112584 B CN103112584 B CN 103112584B CN 201210409284 A CN201210409284 A CN 201210409284A CN 103112584 B CN103112584 B CN 103112584B
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- Prior art keywords
- attachment means
- hub assembly
- amortisseur
- rotor
- pitch
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- 230000009977 dual effect Effects 0.000 title abstract description 12
- 238000000034 method Methods 0.000 claims abstract description 13
- 239000012530 fluid Substances 0.000 claims description 33
- 238000013016 damping Methods 0.000 claims description 9
- 238000007789 sealing Methods 0.000 claims description 8
- 239000006096 absorbing agent Substances 0.000 claims description 6
- 230000000694 effects Effects 0.000 claims description 6
- 238000004891 communication Methods 0.000 claims description 3
- 239000013536 elastomeric material Substances 0.000 claims description 3
- 230000003313 weakening effect Effects 0.000 claims 1
- 230000008859 change Effects 0.000 description 5
- 241001125879 Gobio Species 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000010008 shearing Methods 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000003321 amplification Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000013013 elastic material Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000003340 mental effect Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/51—Damping of blade movements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
- B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
- B64C27/635—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical specially for controlling lag-lead movements of blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49332—Propeller making
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Fluid-Damping Devices (AREA)
- Tires In General (AREA)
- Vibration Dampers (AREA)
- Toys (AREA)
- Mixers Of The Rotary Stirring Type (AREA)
Abstract
The invention discloses a kind of for controlling rotor blade relative to the rotor hub assembly of the motion of pitch and method.Hub assembly has the attachment means of association operable with rotor blade and pitch.This attachment means provides the blade motion of the pivot relative to pitch and rotation.Dual spring ratio amortisseur and the operable association of attachment means.Awing, amortisseur switches to control the motion of rotor blade between the first spring constant and the second spring constant.The method is included in and switches amortisseur in-flight between the first spring constant and the second spring constant.
Description
Technical field
The application relates generally to rotor hub assembly, and has amortisseur more particularly, to one
Rotor hub assembly.
Background technology
Traditional rotor hub assembly be known in the art for efficiently controlling determining of gyroplane
To movement.Hinged hub assembly includes two or more overturning independently of one another, and level is outstanding to be turned, and guides,
And shimmy rotor blade.Hub assembly typically comprises falling hinger, is referred to as turnover hinge, its
Permission blade moves up and down.This motion is referred to as upset and is designed to make up the most right of lift
Claim.Vertical hinge, is referred to as putting/shake (lead/lag) or resistance hinge, it is allowed to blade moves forward and backward.
This motion is referred to as putting/shaking, towing, or driftage.
Traditional rotor hub assembly typically comprises subtracting of association operable with level and/or vertical hinge
Shake device.Amortisseur compensates for the acceleration and deceleration awing produced by rotor.Specifically, amortisseur is joined
Be set to absorb rotor blade power and by put/shake motion frequency maintain desired within the scope of.
Traditional amortisseur includes single damping ratio, and this is undesirable under different flying conditions.
Such as, being selected as the spring constant for putting/shake amortisseur is the value needed for desired in-plane stiffness and reduction
The compromise value being applied between load and the value of fatigue on rotor and other aircraft component.
Although rotor hub assembly has had a great development, however it remains many shortcomings.
Accompanying drawing explanation
It is considered as that the novel features of the characteristic of the present invention proposes in the appended claims.But,
The present invention itself, the most preferred application model, and further object and advantage are by with reference to following
Describe and combine accompanying drawing acquisition in detail to be best understood by, wherein:
Fig. 1 is the side view of the gyroplane of the rotor hub assembly using the application；
Fig. 2 is the oblique view of the tilt rotor aircraft of the rotor hub assembly using the application；
Fig. 3 is the oblique view of the rotor hub assembly of the application；
Fig. 4 is the zoomed-in view of the rotor hub assembly of Fig. 3；
Fig. 5 is the rotor hub assembly zoomed-in view along V-V direction of Fig. 4；
Fig. 6 is the zoomed-in view of the attachment means of the rotor hub assembly of Fig. 4；
Fig. 7 is the top cross-sectional view of the dual spring ratio amortisseur of the rotor hub assembly of Fig. 4；
Fig. 8 is the flow chart describing preference pattern.
Although the system and method for the application can have various deformation and alternative form, its concrete enforcement
Mode is illustrated by the example in figure and is here described in detail.However, it should be understood that
Here the description to detailed description of the invention is not that the application is defined in disclosed particular implementation, and
On the contrary, its purpose is to cover the technique falling into the application being defined by the claims appended hereto
Spirit and scope within all deformed, equivalent, and substitute scheme.
Detailed description of the invention
The hub assembly of the present invention and the illustrative embodiments of method are provided below.It is of course possible to consciousness
In the evolution at any actual embodiment, need to make various decision to realize depending on concrete condition
The specific objective of developer, such as, obey the relevant constraints relevant with business of system, and it is from one
Plant embodiment and change to another kind.Further, it will be appreciated that be that this development makes great efforts to be probably complexity
With time-consuming, but what the those of ordinary skill in the art remaining the interests enjoying the disclosure were subjected to
Conventional process.
The rotor hub assembly of the application overcomes the common shortcoming being associated with traditional components.Specifically
Ground, hub assembly provides the centrifugal force for controlling rotor blade awing, upset, and level is outstanding to be turned,
And put/shake motion.This assembly includes an attachment means, and hereinafter referred to as " gudgeon ", it pivots
Ground and rotatably rotor blade is connected to pitch.The dual spring ratio of association operable with gudgeon
Amortisseur allows awing to carry out selectivity switching between two or more spring constants.These features
Thering is provided for controlling the centrifugal force awing produced by rotor blade, upset, level is outstanding to be turned, and pendulum
The efficient apparatus of/motion of shaking.
The assembly of the application and the structure of method and operation will be managed by the description appended by accompanying drawing combination
Solve.There has been described the several embodiments of this system.Should be understood that the various of different embodiment
Assembly, parts, and feature can be combined and/or exchange each other, even if not having in the accompanying drawings
Whole deformation and detailed description of the invention are shown, within it is entirely located in scope of the present application.Also should manage
Solve be the feature between various embodiment, element, and/or function mixing with mate the brightest
Really consider so that those of ordinary skill in the art are from the feature of disclosed a kind of embodiment, element,
And/or function is it can be appreciated that they can be attached in another embodiment rightly, unless with it
He describes mode.
Referring now to accompanying drawing, wherein identical in various views tab character represents corresponding or similar unit
Part, Fig. 1 and 2 illustrates two kinds of different gyroplanes of the rotor hub assembly using the application.Fig. 1
Illustrating the side view of helicopter 101, Fig. 2 illustrates the oblique view of tilt rotor aircraft 201 simultaneously.Rotor
Hub assembly is preferably used in gyroplane；However, it can be appreciated that feature disclosed herein can be held
Change places and be applicable to other type of aircraft and/or machine.
Helicopter 101 includes the rotor hub assembly 103 carried by fuselage 105.With rotor hub assembly
One or more rotor blades 107 of 103 operable associations provide flight and by position for helicopter 101
Control in the multiple controllers within fuselage 105.Such as, awing, pilot can operate circulation
Controller 109, for changing the angle of pitch and/or the operating pedal 111 of rotor blade 107, thus provides
Vertical, level, and yawed flight motion.
Tilt rotor aircraft 201 includes two or more rotor hub assembly carried by rotatable engine cabin
203.Rotatable engine cabin is provided with for allowing aircraft 201 takeoff and landing as conventional helicopters
And as traditional fixed wing airplane the device of horizontal flight.It should be understood that and helicopter 101
Equally, tilt rotor aircraft 201 is provided with the controller of the movement for controlling aircraft, such as, circulate control
Device processed and pedal.
Fig. 3 depicts the oblique view of the rotor hub assembly of the preferred implementation according to the application.Rotor
Hub assembly 301 efficiently controls the movement produced by rotor blade, such as, puts/shakes, centrifugal force, water
Flat outstanding turn, and upset.It should be understood that rotor hub assembly 103 and 203 disclosed above includes
The feature of rotor hub assembly 301.Thus, it should be understood that rotor hub assembly 301 disclosed herein
Feature can be incorporated into helicopter, tilt rotor aircraft, and other type of gyroplane assembly
In, including aircraft and/or other type of machine.
Rotor hub assembly 301 includes at least two rotor blade of association operable with pitch 305
303.In operation, aeroengine (not shown) drives rotor blade 303, and pitch 305 is controlled simultaneously
The movement of rotor blade 303 processed.In typical embodiment, rotor hub assembly 301 includes six
Rotor blade 303, they rotate along axle A1；However, it can be appreciated that rotor hub assembly is permissible
Including more or less of blade, this depends on preferably applying.Rotor hub assembly 301 also include with
One or more control connections 307 of the operable association of pitch 305, are used for controlling rotor blade 303
Movement.It should be understood that and control to connect and the one or more controllers here discussed and/or control
System links together.E.g. one rotating plasma hub cap of housing 309, is used for protecting pitch 305 and rotation
Other assembly of wing hub assembly 301.In a preferred embodiment, assembly 301 is hinged rotor
Hub assembly, it allows rotor blade to move freely；However, it can be appreciated that the feature of assembly 301 can
To be readily incorporated in other type of hub assembly, including non-articulated assembly.
For the ease of describing, do not illustrate all required subsystem and with rotor hub assembly 301
The device of operable association.Such as, in order to clearly describe the novel features of rotor hub assembly, must
The sensor wanted, adapter, power supply, to install and support, circuit, software, control system etc. is not
Illustrate.It should be understood, however, that as in the art generally well known to, although not discussion
Describe the most in the accompanying drawings, rotor assemblies disclosed herein and these assemblies and needed for other runs
System and the operable association of device.
Referring now to Figure 4 and 5, it is shown that the oblique view of the amplification of rotor hub assembly 301.Fig. 5 is figure
4 along the zoomed-in view in V-V direction, and removes the one of rotor hub assembly 301 for clarity
A little parts.
Pitch 305 preferably includes top driving dish 311 and bottom driving dish 313, two driving dishes
It is used for revolving vane 303.Attachment means 315 is selectively placed between two driving dishes, and
It is configured to be connected to pitch 305 pivotally and rotatably by rotor blade 303.Preferred embodiment party
In formula, attachment means 315 is the gudgeon being formed as T-shape.
Attachment means 315 has rotation and pivoting device, and this rotation and pivoting device make rotor blade 303
Awing slightly revolve on the direction relative to axle A2 due to pendulum/power of shaking of being produced by rotor blade
Turn, and awing slightly pivot on the direction relative to axle A3 due to the upset of rotor blade.
In a preferred embodiment, pitch 305 includes that thickness the first port extending through upper disc (does not shows
Go out) and extend through the second port (not shown) of thickness of lower disc.The two port all configures use
In the end accommodating attachment means.The two port is preferably round, thus allows attachment means to exist
D1 side rotates up along axle A2, and it goes out with arrows.
Preferred embodiment uses the pitch with two driving dishes and circular port to allow to connect dress
Put and rotate.It will be appreciated, however, that the substituted device of the gudgeon for rotating relative to pitch,
Equally it is used in the embodiment replacing preferred embodiment.Such as, pitch can use and can
Rotor blade is connected on pitch by the single driving dish of the operable association of rotating hinge module.But,
It can be appreciated that preferred embodiment has significant advantage, including the support added and rigidity.
Rotor hub assembly 301 farther includes the centrifugal bearing 317 supported by rotor yoke boom 319
(hereinafter referred to as " C.F. bearing ") and one of association operable with attachment means 315 or many
Individual dual spring ratio amortisseur.In a preferred embodiment, C.F. Bearing configuration becomes to control by rotor blade
The centrifugal load produced, dual spring ratio shock-absorber configuration becomes to be selectively controlled in in-flight by revolving simultaneously
Pendulum/motion of shaking that wing blade produces.
In an exemplary embodiment, rotor hub assembly 301 includes two dual spring ratio amortisseurs: logical
Cross upper arm 322 and be fixed firmly to the first amortisseur 321 of upper disc 311 and by underarm 324 jail
Admittedly be fixed to the second amortisseur 323 of lower disc 313.Awing, dual spring ratio amortisseur choosing
Change between the first spring constant and the second spring constant to selecting property.Such as, shock-absorber configuration becomes to provide
Hard and soft damping ratio.This feature is especially needed in tilt rotor aircraft, because amortisseur is permissible
It is switched in helicopter mode produce from the lock arrangement producing rigidity hub assembly airplane-mode
The unblock configuration of softer hub assembly.In certain embodiments, airplane-mode typically requires rigidity
Face in configuration remain stable in the speed of about 160 joints, and need in helicopter mode
Avoid the ground resonance problem produced due to wing and suspension bracket frequency.
It should be understood that flip-flop movement upset controller by use full authority in airplane-mode
(not shown) and realize minimizing, upset controller vert pitch on one's own initiative upset to be limited in not
More than 8 degree.Upset needs the rotor being minimized to minimize in rigid arrangement with being turned into ratio to bear
Carry.Need configuration in soft face to reduce the hub occurred in strong switching process in helicopter mode to bear
Carrying, strong upset occurs in the manipulation of helicopter mode.The duty factor limiting upset in articulation pattern exists
In rigid mode much lower.Peak value upset usually occurs in high-speed helicopter operation.
Fig. 6 illustrates the oblique view of attachment means 315.In a preferred embodiment, attachment means 315 is made
Causing and have T-shape, it has relatively vertically extending with two side arms 603 and 605 the most main
Body 601.Main body 601 includes two relative ends being configured to be rotatably connected to pitch；The
One end 607 is configured to be connected with the port extending through upper disc 311 and the second end 609 is configured to
It is connected with the port extending through lower disc 311.First and second ends are provided with rotary apparatus for the company of making
Connection device 315 rotates relative to pitch 305.As it can be seen, the first and second ends are preferably circle
Oblique crank Z element, is configured to extend through and be connected to the port of upper and lower driving dish.It it is to be appreciated that
Elastomeric material can be placed between end and port, so that attachment means 315 is raw relative to driving hair updo
Slight elastic rotation.
Attachment means 315 includes the bearing arrangement 611 with at least three bearing: carried by side arm 603
Clutch shaft bearing 613, side arm 605 the second bearing 615 carried, and being arranged in main body 601
3rd bearing 617 in portion.Bearing arrangement 611 allows upset, level is outstanding turn and put/shake motion simultaneously to from
Mental and physical efforts and hub shearing force generation effect.Bearing arrangement provides in thru-flight pattern and is connected to rotor mast
Being rigidly connected of bar (not shown), allows upset and the outstanding transhipment of level dynamic simultaneously.In preferred embodiment
In, bearing 613 and 615 is sliding bearing, and bearing 617 is spherical bearing.Three whole bearings
Along axle A3 arranged in co-axial alignment and be configured to accommodate axle 619.Axle 619 is provided with for allowing yoke arms
319 relative to the rotary apparatus of the pivoting action of attachment means 315.When assembled, yoke arms 319
It is connected to attachment means 315, so that rotor blade can be sent out relative to hub assembly by axle 619
Raw flip-flop movement.
Referring to Fig. 7, it is shown that the cross-sectional view of the inner top of amortisseur 321.For the ease of describing,
Only being described in detail in two amortisseurs, amortisseur 321 is shown and described below.So
And, it should be understood that amortisseur 323 includes whole features of amortisseur 321.
As discussed earlier, the two dual spring ratio shock-absorber configuration becomes awing at the first spring ratio
Optionally switch between rate and the second spring constant.First spring constant is optionally arranged by multiple
Flexible member in amortisseur produces, and is applied to flexible member along with revolving force and produces desired cutting
Cut resistance.It is to be appreciated that the elastic characteristic of elastomeric material can according to preferably application optionally
Design is to produce desired shearing resistance.Second spring constant is arranged in amortisseur with being positioned at by multiple
Two fluid containers between the flexible member that links together of fluid passage and produce.These features
Describe and be shown in and be given below.
Amortisseur 321 includes the non-rotating enclosure body being strongly attached to driving dish in top by arm 322
701.Shell body 701 accommodates flexible member and one or more fluid for producing dual spring ratio
Chamber.In an exemplary embodiment, amortisseur 321 includes four for the stream producing desired damping effect
Body cavity；But, alternative embodiment, according to preferably application, can include more or less of fluid cavity.
It is a kind of incompressible fluid, such as, hydraulic fluid with fluid in a preferred embodiment, oil and/or replace
The suitable fluid in generation.
Amortisseur 321 farther includes to be rotatably connected to by multiple elastic sealing elements 705 and 706
The inner housing 703 of shell body 701.The end 607 of attachment means 315 is by being arranged between
Elastic sealing element 707 is connected to inner housing 703.Elastic sealing element is along with attachment means 315 is relative to subtracting
Shake device 321 applies rotary motion and produces the first spring constant.
In a preferred embodiment, four fluid tight chamber 709 produce between two housings.As under
Face describes in further detail, and these chambeies are configured to produce the second spring constant.For the ease of describing, right
One in four chambeies is described in detail；It should be understood, however, that four chambeies are in form and functionally
Identical.
Chamber 709 includes at least two container: the first container 711 and the second adjacent container 713, two appearances
Device passes through pipeline 715 fluid communication with each other.In an exemplary embodiment, housing 701 it is elastically connected to
Blade 717 separates the two fluid container.Should realize is that pipeline 715 can in alternative embodiments
With through blade 717.
Being in operation, blade 717 moves in container, so that liquid exchanges between containers.Valve
719 limit fluid circulation in pipeline 715.Upon closing, flow through the fluid of pipeline limited and
Blade movement in fluid container is prevented from.In this case, damping effect is only by being arranged on damping
Elastic sealing element in device produces.When open, fluid circulates in two containers and blade is allowed to
Move in container.In this case, generation the second spring ratio is exchanged between the two containers along with fluid
Rate and softer damping.
In a preferred embodiment, valve 719 is configured to fully open and cut out the passage by pipeline 715；
However, it can be appreciated that alternate embodiment can include allowing have selective flowing by pipeline 715
The valve of ratio.Such as, ball valve or slide-valve can be as the most fully changing
Valve.
Valve 719 open and close control by one or more in fuselage perform Artificial Control and/
Or realized by automatically controlling of performing of aircraft control system.Such as, softer damping effect is being expected
Under flying condition, valve 719 allows fluid only to control switch (not shown) by operation one and flow through pipe
Road 715, and same, and when the hardest damping effect, valve 719 can be by operation
Same switch limits fluid and flows through pipeline 715, and switch both can artificially control automatically to control
System.The opening and closing of valve 719 can be electronic by hydraulic pressure, or machinery realizes.
In a preferred embodiment, elastic sealing element 705 is preferably made into has " sandwich " structure,
Elastomeric layer and rigid layer, non-elastic material, such as metal level are alternately arranged.Such structure
On the direction being generally perpendicular to each layer the most incompressible, allow the shearing of predefined size simultaneously
Motion.
With reference to Fig. 8, it is shown that describe the flow chart 801 of preferred method.Square frame 803 describes and will connect
Device is connected to pitch.As described at square frame 805, attachment means provides the rotation being connected thereto
The pivot of wing blade and rotary motion.Then, as described in square frame 807, dual spring ratio amortisseur quilt
It is connected to attachment means.Finally, square frame 809 describes awing at the first spring constant and the second bullet
Change between spring ratio.
It is evident that the described herein and assembly of diagram and method have significant advantage.It is disclosed above
Detailed description of the invention simply schematically, embodiment can be modified and with to the religion enjoyed here
But the mode of different equivalences is implemented for the those skilled in the art of the interests led.It is therefore evident that
It is that particular embodiments disclosed above can change and revise, and whole deformation is considered to be positioned at
Within scope of the present application and spirit.Therefore, protection sought herein proposes in the description.On although
Face shows existing embodiment, and they are not limited in these embodiments, but revisable,
And variations and modifications are all without departing from spirit herein.
Claims (11)
1. for a rotor hub assembly for gyroplane, including:
Pitch；
Attachment means, is rotatably connected to pitch and is pivotably connected to rotor blade, described
Attachment means has the first end and the second end；And
First amortisseur of association operable with attachment means, the first shock-absorber configuration becomes at the first spring ratio
Optionally switch between rate and the second spring constant, and the first amortisseur is configured to weaken in flight
In the power that applied by rotor blade；Described first amortisseur is fixed on described the first of described attachment means
On end and described pitch, described first amortisseur includes:
Fluid tight chamber, it has:
First fluid container；
Second fluid container；And
The pipeline being in fluid communication with described first fluid container and described second fluid container；
With the valve of described fluid communication, described valve is configured to be limited in described first fluid container
And the fluid passage between described second fluid container；
Elastic sealing element, be placed on the end of described attachment means main body and driving dish port it
Between, and it is configured to the rotary motion flexibly stoping described attachment means relative to described pitch；
Wherein said first spring constant is produced by the elastic resistance from described elastic sealing element, stream
Body is limited by described pipeline；And
Wherein said second spring constant is produced by the elastic resistance from described elastic sealing element, and
And fluid passes through between described first fluid container and described second fluid container；
Second amortisseur of association operable with described attachment means, and the second amortisseur is configured to subtract
The weak power awing applied by rotor blade；Described second amortisseur is fixed on described attachment means
On described second end and described pitch.
2. rotor hub assembly as claimed in claim 1, farther includes:
Second amortisseur of association operable with attachment means, the second shock-absorber configuration becomes at the first spring ratio
Optionally switch between rate and the second spring constant, and the second shock-absorber configuration becomes to weaken from rotor
The power of blade.
3. rotor hub assembly as claimed in claim 1, farther includes:
The centrifugal bearing of association operable with rotor blade；
The most centrifugal Bearing configuration becomes to weaken the centrifugal force from rotor blade.
4. rotor hub assembly as claimed in claim 1, pitch includes:
Top driving dish；And
Bottom driving dish；
Wherein attachment means is arranged between top driving dish and bottom driving dish；And
Wherein attachment means is rotatably connected to top driving dish and bottom driving dish.
5. rotor hub assembly as claimed in claim 1, attachment means includes: held by attachment means
Carry and be configured to be pivotably connected to rotor blade the bearing arrangement of attachment means.
6. rotor hub assembly as claimed in claim 5, bearing arrangement includes:
Axle；And
It is configured to accommodate the bearing of axle；
Wherein rotor blade is connected to axle and is pivoted relative to attachment means by bearing.
7. rotor hub assembly as claimed in claim 1, attachment means includes:
Longitudinal main body；
First arm and the second arm, two arms are connected to longitudinal main body and extend out from longitudinal main body；
The bearing arrangement carried by the first arm and the second arm；And
The axle being pivotably supported by the first arm and the second arm by bearing arrangement；
Wherein rotor blade is connected to axle and pivots relative to attachment means by bearing arrangement.
8. rotor hub assembly as claimed in claim 7, pitch includes:
Top driving dish；And
Bottom driving dish；
Wherein longitudinal main body is rotatably connected to top driving dish and bottom driving dish.
9. a method, including:
Rotor hub assembly described in claim 1 is provided；
Attachment means is rotatably connected to pitch, and attachment means is configured to spiral relative to inclination
Turn；
Rotor blade is pivotally connected to attachment means, and rotor blade is configured to relative to attachment means pivot
Turn；
Amortisseur is used to weaken the rotary motion of attachment means；And
Awing, between the first spring constant and the second spring constant, damping effect is switched.
10. method as claimed in claim 9, wherein the switching of flexible ratio is arranged on by control and subtracts
Shake the fluid passage between two fluid containers in device and realize.
11. methods as claimed in claim 10, wherein the weakening by being arranged on amortisseur of rotary motion
In elastomeric material realize.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/298,033 | 2011-11-16 | ||
| US13/298,033 US9126680B2 (en) | 2011-11-16 | 2011-11-16 | Dual mode rotor hub assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103112584A CN103112584A (en) | 2013-05-22 |
| CN103112584B true CN103112584B (en) | 2016-09-14 |
Family
ID=45400986
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210409284.0A Expired - Fee Related CN103112584B (en) | 2011-11-16 | 2012-10-24 | dual mode rotor hub assembly |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US9126680B2 (en) |
| EP (2) | EP2594483B1 (en) |
| CN (1) | CN103112584B (en) |
| CA (1) | CA2794039C (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108069030A (en) * | 2016-11-18 | 2018-05-25 | 贝尔直升机德事隆公司 | For the propulsion rotor system of tiltrotor aircraft |
Families Citing this family (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9352830B2 (en) * | 2012-04-25 | 2016-05-31 | Textron Innovations Inc. | Aircraft rotor with discrete flap hinge |
| US9656744B2 (en) * | 2014-05-21 | 2017-05-23 | Bell Helicopter Textron Inc. | Adjustable blade-to-hub lead-lag damper attachment |
| WO2017094440A1 (en) * | 2015-12-02 | 2017-06-08 | 三菱日立ツール株式会社 | Hard coating, hard coating-covered member and manufacturing method therefor, and target used for producing hard coating and manufacturing method therefor |
| US10232932B2 (en) | 2017-03-22 | 2019-03-19 | Bell Helicopter Textron Inc. | High stiffness hub assembly for proprotor systems |
| US10457380B2 (en) * | 2017-06-28 | 2019-10-29 | Bell Textron Inc. | Articulated rotor systems with pitch independent damping |
| US10486807B2 (en) | 2017-07-13 | 2019-11-26 | Bell Textron Inc. | Inboard bearing assemblies having independent shoes |
| US10507912B2 (en) | 2017-07-13 | 2019-12-17 | Bell Textron Inc. | Inboard bearing assemblies with improved accessibility |
| US10514060B2 (en) | 2017-07-13 | 2019-12-24 | Textron Innovations Inc. | Inboard bearing assemblies with anti-rotation features |
| US10479497B2 (en) | 2017-07-13 | 2019-11-19 | Bell Textron Inc. | Inboard bearing assemblies having load transfer shoe bolts |
| US10494091B2 (en) | 2017-07-13 | 2019-12-03 | Bell Textron Inc. | Hub bolt supported inboard bearing assemblies |
| US10472059B2 (en) | 2017-07-13 | 2019-11-12 | Bell Textron Inc. | Inboard bearing assemblies for proprotor systems |
| US11027834B2 (en) | 2018-02-22 | 2021-06-08 | Textron Innovations Inc. | Inboard centrifugal force bearing attachment |
| US10597150B2 (en) | 2018-04-24 | 2020-03-24 | Textron Innovations Inc. | Articulated rotor systems with blade-to-blade damping |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2774553A (en) * | 1955-04-04 | 1956-12-18 | United Aircraft Corp | Damper by-pass for lag-lead control of helicopter rotor blades |
| US3134444A (en) * | 1961-08-23 | 1964-05-26 | Kaman Aircraft Corp | Aircraft rotor-propeller |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4543040A (en) * | 1982-09-30 | 1985-09-24 | The Boeing Company | Helicopter rotor system |
| FR2592449B1 (en) | 1985-12-30 | 1989-12-08 | Aerospatiale | ROTATION SHOCK ABSORBER |
| US5501434A (en) * | 1994-05-10 | 1996-03-26 | Lord Corporation | Hybrid fluid and elastomer damper |
| US6889965B2 (en) * | 2001-10-10 | 2005-05-10 | The Boeing Company | Opposing conical preloaded elastomeric bearing assembly |
| US6758466B2 (en) * | 2002-11-06 | 2004-07-06 | Lord Corporation | Fluid-elastomeric damper assembly including internal pumping mechanism |
| FR2848524B1 (en) * | 2002-12-13 | 2005-12-09 | Eurocopter France | CYCLIC TRAY DEVICE FOR CONTROLLING THE PITCH OF THE BLADES OF A ROTOR OF GIRAVION |
| CA2533523C (en) | 2003-08-27 | 2010-03-30 | Bell Helicopter Textron Inc. | Soft in-plane rotor hub |
| CN101472793B (en) * | 2006-06-20 | 2013-07-24 | 贝尔直升机泰克斯特龙公司 | Centrifugal force bearing with stabilizing pronation suppress force moment |
| US8413772B2 (en) | 2008-02-12 | 2013-04-09 | Techno-Sciences, Inc. | Magnetorheological fluid elastic lag damper for helicopter rotors |
| FR2954274B1 (en) * | 2009-12-17 | 2012-02-24 | Eurocopter France | VIBRATION DAMPER MECHANISM, AND FLYING APPARATUS PROVIDED WITH A CARRIER STRUCTURE AND A ROTOR HAVING SUCH A MECHANISM |
| FR2957998B1 (en) | 2010-03-29 | 2013-04-26 | Eurocopter France | DAMPER OF A BLADE, AND ROTOR PROVIDED WITH SUCH SHOCK ABSORBER |
-
2011
- 2011-11-16 US US13/298,033 patent/US9126680B2/en active Active
- 2011-12-22 EP EP12175816.3A patent/EP2594483B1/en active Active
- 2011-12-22 EP EP11195396.4A patent/EP2594482B1/en active Active
-
2012
- 2012-10-24 CN CN201210409284.0A patent/CN103112584B/en not_active Expired - Fee Related
- 2012-11-01 CA CA2794039A patent/CA2794039C/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2774553A (en) * | 1955-04-04 | 1956-12-18 | United Aircraft Corp | Damper by-pass for lag-lead control of helicopter rotor blades |
| US3134444A (en) * | 1961-08-23 | 1964-05-26 | Kaman Aircraft Corp | Aircraft rotor-propeller |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108069030A (en) * | 2016-11-18 | 2018-05-25 | 贝尔直升机德事隆公司 | For the propulsion rotor system of tiltrotor aircraft |
| CN108069030B (en) * | 2016-11-18 | 2021-04-20 | 德事隆创新公司 | Propulsion rotor system for tiltrotor aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2594482A1 (en) | 2013-05-22 |
| CA2794039C (en) | 2016-01-19 |
| EP2594483B1 (en) | 2014-09-24 |
| US9126680B2 (en) | 2015-09-08 |
| US20130121827A1 (en) | 2013-05-16 |
| EP2594483A1 (en) | 2013-05-22 |
| EP2594482B1 (en) | 2015-03-18 |
| CA2794039A1 (en) | 2013-05-16 |
| CN103112584A (en) | 2013-05-22 |
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